Abstract
The SAO project aims at providing large wind tunnel users with benefits from improvements achieved in the numerical codes for flow fields. The idea is to improve the accuracy of measurement data in the wind tunnel by evaluating the various bias of the experimental simulations in the wind tunnel. One of the applications is the calculation of support interference effect. The aerodynamic interf erence effects of usual devices supporting aircraft models during wind tunnel tests have been studied by means of steady RANS simulations of the flow. The flow field and force d isturbance caused by the supports were calculated by comparing simulations with and without support. Two configurations were addressed, both with transonic test of a civil airc raft model. The first analyze the model mounted on a straight sting, the second one concent rates on fin sting effects. The support effect is analyzed for several Mach numbers and angles of attack. Special attention was paid to the proper derivation of corrections of the inco ming flow conditions in terms of Mach number and angle of attack. Comparison against experimental data is provided to validate the results.
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